Fan-pump.



. H. KLEC-KLER.

F AN PUMP.

'APPHCATION FILED NOV. 17, l9l6- Patented N 0V; .5, 1918.. 3 SHEETSSHEETI HENRY KLECKLER.

H. KLECKLER.

FAN PUMP.

APPLICATION FILED NOV. 17, 1916.

1 ,283,529. Patented Nov. 5,- 1918.

3 SHEETS-SHEET 2.

KLECKLER I APPLICATION FILED NOV. 17. 1916. v 1,283,529. Patented Nov.5,1918.

3 $HEET5 SHEET 3.

54: aM uq tz i HENRY KL 8% Ga a UNITED STATES PATENT OFFICE.

HENRY KLECKLER, 0F BUFFALO, NEW YORK, ASSIGNOR T0 CURTISS AEROPLANE ANDMOTOR CORPORATION, A CORPORATION OF NEW YORK.

FAN-PUMP.

I Specification of Letters Patent.

Patented Nov. 5, 1918.

Application filed November 17, 1916. Serial No. 131,964.

New York, have invented certain new and useful Improvements inFan-Pumps, of which the following is a specification.

My invention relates to aircraft and has reference more particularly toequipment therefor consisting of an improved Wind driven ,fecdpumpingsystem.

In the aeronautical art, and especially in hydroaeroplanes and flyingboats, it is customary to locate the motor or propelling power plantwithout and in a horizontal plane above the hull or body of the machine.The fuel supplied to the motor is fed by gravity from an elevatedgravity feed tank seated thereabove preferably intermediate thesuperposed supporting surfaces or planes. Another and much larger tankis located interiorly of the hull. From the latter, a storage tank, thefuel is pumped during flight continuously or uninterruptedly into thegravity feed tank. It is to the latter end, i. e. the pumping feature,that the present invention is designed.

The pumping unit, in its preferred embodiment, may be generally.described as comprising a housing, a pumping element, and a fan or pumpdriving means. The housing in its entirety is located and fastenedinteriorly of the fuel storage tank with its bottom end in engagementwith the tank bottom and its top end in engagement with the tank top.Being liquid-tight, the housing affords an inelosure for the pumpingunit which at one endis extended thereinto. The opposite end of thepumping unit is extended well beyond the deck of the hull for exposureat a point in the direct path of air rush during flight. It is at thisend of the pumping unit that the fan or pump driving means is mounted. Apartition. removable with the pump, subdivides the housing horizontallyinto non-communicating compartments, the lower compartment afiording anoperating space for the pumpproper and the upper compartment anaccessible inclosure of a-size permitting repair, if necessary, of theinclosed pump parts. Openings are formed at the bottom end of thehousing. Should occasion demand, the pumping unit in its ensemble may beremoved and replaced without soiling or wetting the hands. An outlet orlead extends from the pump proper to the gravity feed tank. Such is thesystem of my invention.

In describing my invention in detail, reference will be had to theaccompanying drawings wherein like numerals of reference designate likeor corresponding parts throughoutthe several views, of which:

Figure l is a side elevation of a hydroaeroplane (partly broken away)equipped with a pumping system or plant in accordance herewith;

' Fig. 2 is a longitudinalsectional view of the pumping unit and itsassociated means;

Fig. 3 is a similar view in which the section is taken at right anglesto that of Fig. 2;

Fig. 4 is a transverse section at the bottom of the pumping unit, and

. Fig. 5 is a detail longitudinal sectional View of the pump proper andthat portion of the pumping unit directly adjacent thereto.

In the embodiment of my invention selected for illustration, 10designates the hull or body of a Curtiss flying boat. Supportingsurfaces 11 including a built-in engine sect-ion panel, fin excrescences12, an a rearwardly. facing step 13, characterize the hull. thercharacteristics such as the fin braces 1&, Wing posts 15 and enginesection panel braces 16 have been disclosed. Preferably the rearwardlyfacing step 13 is formed in the hull bottom in the vicinity of avertical line projected through the center of ravitiy. l

gich a construction and arrangement of parts as I have already disclosedis only preferred and may be modified considerably without departingfrom the spirit of the invention as claimed.

Fuel storage tanks, three in'number, designated respectively 17, 18 and19, are located interiorly of 'the hull symmetrically as regards thecenter of gravity. Preferably all variable load is thus located. Thetanks 17 and 19 are slightly elevated with respect to the tank 18 topermit of gravity feed thereto. This arrangement will necessitate theemployment of but a single pumping unit and yet permit of fore and afttank adjustment should such adjustment become necessary in balancing themachine.

The motor or propelling power plant (not shown) as stated, is locatedwithout the hull being above that of the motor. Leads (not shown) extendfrom the gravity feed tank to the motor. I

Since the gravity feed tank is located above the fuel storage tanks andsince the motor fed directly from the gravity feed tank, it is evidentthat a means must be installed whereby the stored fuel contained in thestorage tanks is transferred, while the machine is in flight to thegravity feed tank. This I accomplish by the pumping plant or systemdesignated in its entirety by the nunieral 21.

In its preferred embodiment, the pumping unit may be generally describedas comprising a housing 22, open ended, cylindrical and of a length toengage at one end in a sump 23 formed at the bottom of the tank 18 andat its opposite end engage with the tank top. An opening 24 somewhatlarger than the housing is formed in the bottom of the tank 18 so thatthe.housing. in assembling, may be passed therethrough. After securementof the housing, the sump 23 is fitted over the opening in the tank. Anannular outwardly directed flange is formed at the bottom of the housingto engage in the sump and afford, in assembling, a centering meanstherefor. If desired, the sump and housing may be made rigid by suitablefas tening means arranged to penetrate both the flange and the sump.Fuel inlet openings 25' are formed in the housing at its lower end.

At its opposite end, the housing '22 is similarly flanged as indicatedat 526, the flange contacting with the end surface of the tank topci-rcumferentially .of an opening 27 formed therein. Fastening devices28,penetrate the flange 26, the tank top, and a washer 29 to secure thehousing in place.

Directly over the housing an opening 30 is formed in the deck of thehull 10. Through this opening, the pumping unit extends without thehull. At a point inte riorly of the housing 22 adjacent the sump thepumping unit terminates. Gears 31 and 32 constitute the pump proper. Thegear 31 is provided with a stud 33, polygonal in cross section, the studengaging in a complemental socket 31 formed in an enlargement of a shaft35 vertically disposed.

Said shaft comprises separable shaft sections designated-respectively 36and 37. The shaft section 36 contacts directly the stud 33 and with theconnected shaft section 37 affords a driving means for the pump gear 31.The gears 31 and 32 are in mesh.

The shaft 35 at its extended terminal is equipped with the pump drivingmeans designated as an entirety by the numeral 38. This means may begenerally described as comprising a fan 39, a fan shaft 10, and a bevelpinion 11. The said shaft 40 is mounted to extend forwardly beyond andwithout an appropriate two-part gear case 42-, the terminals of the gearcase affording bearings for said shaft. From the pinion 41, motion istransmitted to the vertical shaft 35 through the medium of a bevel gear43 mounted on said shaft. Both the gear 43 and the pinion 41 areinclosed within the gear case. The sections 36 and 37 which constitutethe shaft 35 are jointed together by means of a sleeve 41 fastened atone end as indicated at 15 to the shaft section 37 and shaped at itsopposite end to receive in its bore a polygonal head l6 formed on theshaft section 36. This construction will permit the pumping unit,excluding the pump proper and its directly associated means to bewithdrawn from the housing 22 if desired.

Removal of the pumping unit in its entirety is made possible by thepeculiar mounting of the pump driving means 38 at the extended terminalof the shaft 35. Up-

rights 46 fastened as indicated at 47 .to a' cover plate 48 support thepump'driving means in its elevated or extended position. The cover plate48 is preferably of a size and shape substantially complemental t0 theannular flange 26 of the housing to which it is indirectly fastenedbyany suitable means.

The shaft, 35, interiorly of the housing, is inclosed in a tube 49extended at one end through the cover plate and at its opposite end intoa recess formed by an upstanding flange 50 integral with a partition 51located interiorly of the housing and adjacent its bottom end. Beneaththe partition 51 the gear case 52 for the pump gears 31 and 32 islocated, the gear casing including in addition to a removable coverplate 53 'an appropriate screening element 54 of a construction designedfor arrangement beneath the cover plate to filter the fuel before itsadmission through the pump inlet opening 55 to the interior of the pump.Bolts 56 pass transversely through the partition 51, the pump casing andthe pump casing cover 53. The bolts 56 also serve as the fastening meansfor the screen 54. When it is desired that the pump case cover plate beremoved without removing the pumping unit in its entirety, access isgained to the bolts 56 by first emptying the tank and thereafterremoving the sump 23. A removable threaded plug 57 is located at thebottom of the sump for draining the tank.

The tube 19 at its opposite end is fastened by any suitable means to anupstanding flange 58 brazed to or integral with the cover plate for thehousing. At its opposite end,

the tube is fastened as indicated at 59 to the upstanding flange 50.Through such an arrangement the cover plate 48 acts as the sole supportfor the entire pumpingunit and the pump driving means. 7

The pump outlet is located at the opposite side of the pump casing fromthat in which the inlet opening 55 is. formed and designated 60. Asindicated in Fig. 4, a lead 61 extends from the outlet opening 60vertically interiorly of the housing to and through the cover plate 48where it'is coupled as indicated at 62 to a flexible lead 63 discharginginto the gravity feed tank 20.

Immediately theaircraft is set in motion, the air rush incident toflight will drive the fan 39. From the fan 39, through theintermediaries 40, 41, 43 and 35, motion is transmitted to the pumpproper, i. e.,the gears 31 and 32. The suction created by the rotatinggears will draw the liquid fuel into the housing 22 below the partition51 through the openings 25, through the screen 54, the inlet opening 55to the interior of the pump casing where it is forced or pumped outthrough the opening 60 and via the leads 61 and 63 to the gravity feedtank 20. From the feed tank the fuel gravitates continu-.

ously and uninterruptedly to the motor or motors. Fuel is thus suppliedto the gravity feed tank at all times while the craft is in flight andthe motor in operation.

To preclude the admission of extraneous matter to the interior of thehousing at the top end of the tube 49, a conical cover 64 rotatable withthe shaft 35 is provided. The basal diameter of the cover is of suchdimension as to extend beyond the upstanding flange 58 to which the tubeis secured and flush with which the tube terminates at its upper end.The partition 51 transversely divides the housing 22 into'non-communleating compartments, the upper or larger compartment beingliquid-tight and of an interior size permitting access thereto withoutwetting or soiling the hands and without disengaging or disassemblingany of the pump parts. To remove the pumping unit in its entirety it isbut necessary that the cover plate 48 be unfastened and bodily liftedwith its various associated elements through the opening 30 in the hullof the craft. As stated, the cover plate 48 affordsthe sole support forthe uprights 46, the pump driving means 38 and the pumping unit. Byreason of the flexible connections indicated at 63, the lead 61 isremovable with the pumping unit. Wherever practical,

the parts may be lightened and if extended without the body of the hull,streamlined.

While in the foregoing there has been illustrated in the drawings anddescribed in the specification such combination and arrangement ofelements as constitute the preferred construction or embodiment of theinvention, it is nevertheless desired to emphasize the fact thatinterpretation of the invention should only be conclusive when made inthe light of the subjoined claims.

What is claimed is:

' 1. In an aircraft, the combination of a fuel storage tank locatedinteriorly of the body of the craft, a gravity feed tank locatedthereabove, and a propelling power plant, of a fuel pumping systemincluding a pumping unit located interiorly of the fuel storage tank, anair driven pump driving means'located exteriorly of the body of thecraft in the direct line of air rush incident to flight, and a conduitleading from the, storage tank to the gravity feed tank for supplyingfuel thereto uninterruptedly during operation of the pump driving means.

2. In an aircraft, the combination with a fuel storage tank locatedinteriorly of the body of the craft, a gravity feed tank located withoutthe body of the craft, and a propelling-power plant, of a fuel pumpingsystem includingapumping unit of a construction designed to extend atone end into the fuel storage tank and at its opposite end without thebody. of-the craft, an air driven pump driving means mounted at theouter extended terminal of said pumping unit and in the direct line ofair rush incident to flight, and a conduit leading from the storage tankto'the gravity feed tank for supplying fuel thereto uninterruptedlyduring operation of the pump driving means.

3. In an aircraft, the combination with a fuel storage tank locatedinteriorly of the body of the craft, a gravity feed tank locatedt-hereabove, and a propelling power plant, of a fuel pumping systemincluding a pumping unit of a construction designed to extend at one endinto the interior of the fuel storage tank and at its opposite endwithout the body of the craft through an opening formed therein, an airdriven pump driving means mounted at the outer extended terminal of thepumping unit and in the direct line of air rush incident to flight, andaconduit leading from the storage tank to the gravity feed tank forsupplying fuel thereto uninterruptedly during operation of the pumpdriving means.

4. In an aircraft, the combination with a fuel storage tank locatedinteriorly of the body of the craft, a fuel supply chamber, and apropelling power plant, of a fuel pumping system including the pumpingunit located interiorly of the fuel storage tank, an air driven pumpdriving means located exteriorly of the body of the craft in the directline of air rush incident to flight, and a conduit leading from thestorage tank to the supplylchamber for supplying fuel theretouninterruptedly during operation of the pump driving means.

5. In a fuel pumping'system, the combination with a fuel storage tankhaving a bottom sump formed therein, of a housing having fuel inletopenings formed therein for disposition at the sump, a pumping unitconstructed to operate interiorly of said housing and to extendtherethrough beyond the top thereof, associated exteriorly located an;driven pump driving means, and a fuel outlet leading from the pump.

6. In an aircraft fuel pumping system, the combination with the fuelstorage tank, of a housing having fuel inlet openings formed therein, apumping unit constructed to operate interiorly of said housing ad acentsaid openings and to extend at one end therewithout, a partitionseparating that portion of the housing having the inlet openings formedtherein from the remainder thereof, associated exteriorly locateddriving means, and a fuel outlet leading from the pump.

7. In an aircraft fuel pumping system, the combination with a fuelstorage tank, of a housing liquid-tight except for fuel inlet openingsformed therein at the bottom end. said housing being submerged into thefuel tank and having the lower part thereof flooded with fuel passingthrough said openings, a pumping unit constructed to operate interiorlyof said housing adjacent said openings and to extend at one endexteriorly thereof, a means maintaining the pumping unit fixed withrespect to said housing, exteriorly located pumpsdriving means, and afuel outlet pipe leading from the pump.

8. In' an aircraft fuel pumping system, the combination with a fuelstorage tank, of a housing liquid tight except for fuel inlet openingsformed therein, a pumping unit constructed to operate interiorly of saidhousing and to extend at one end considerably therewithout, a. meansdually functioning topartition the housing and preclude displacement ofthe pumping unit, pump driving means mounted at the outer extendedterminal of said pumping unit, and a fuel outlet pipe leading from thepump.

9. In an aircraft fuel pumping system, the combination with a fuelstorage tank, of a housinn; liquid-tight except for fuel inlet openingsformed therein, pumping means operable within said housin adjacent saidopenings and of a construction designed to extend therethrough andbeyond the top thereof, said pumping means being removable from thehousing as a unit, driving means for the pump located without thehousing, and a fuel outlet pipe leading from the pump.

10. In an aircraft fuel pumping system, the combination with a fuelstorage tank, of a. housing liquid-tight except for fuel inlet openingsformed therein at its bottom end, a bodily removable pumping unit of aconstruction designed to operate interiorly of said housing adjacentsaid openings and to extend at its opposite end without the housing, andair driven pump-driving means mounted at the extended terminal of thepumping unit.

11. In an aircraft fuel pumping system, the combination with a fuelstorage tank, of an open ended housing liquid-tight exceptfor fuelopenings formed therein at its bottom end, a bodily removable pumpingunit of a construction designed to operate inte riorly of said housingadjacent said openings and to extend at its opposite end therewithout,pump-driving means mounted at the extended terminal of the pump unit. acover plate for the housing removable with the pumping unit, and a fueloutlet pipe leading from the pump.

In an aircraft fuel pumping system. the combination with a fuel storagetank, of an open ended housing liquid-tight except for fuel openingsformed therein at its bottom end, the housing at said bottom enddirectly contacting with the bottom of the tank, a cover plate for theopposite end of the housing adapted for securement to the tank, apumping unit constructed to operate interiorly of the housing adjacentsaid openings and to extend at its opposite end through the cover plate,and pump driving means mounted at the extended terminal of the pumpingunit, the cover plate and the driving means being removable with thepumping unit in disassembling the pump.

13. "In an aircraft fuel pumping system, the combination with the fuelstorage tank, of a housing having openings formed therein at its bottomend, a cover plate. for the housing. a pumping unit constructed tooperate interiorly of said housing adjacent said opening and. to extendtherewithout through the cover plate, pump driving means mounted at theextended terminalv of the pumping unit, a support for the driving meansmounted on the cover plate, a partition for separating that portion of.the pumping unit adjacent said openings from the remainder thereof, anda fuel outlet pipe leading from the pump, the said outlet pipe,partition, driving means. support, and cover plate being removable as aunit with the pumping means in disassembling the pump.

14. In an aircraft fuel pumping system. the combination with a fuelstorage tank having a sump formed in the bottom thereof, an open endedhousing mounted interiorly of the tank to engage at one end with thetank bottom at the sump and at its opposite end to register with anopening formed in the tank top, a pumping unit' constructed to operateinteriorly of the housing adjacent said opening and to extend therewithout through the open top, a pump-driving means mounted at theextended termiriorly of the tank, a pumping unit on structed to operateinteriorlyof said hous ing and to extend therewithout, a pump-' drivingmeans mounted at the extended terminal of the pumping unit, andascreening element removable with the pump.

16. In an aircraft fuel pumping system,

, the combination of a fuel storage tank, lo-

cated-interiorly of the body of the craft, a

propelling power plant, and a fuel pumping unit comprising a rigidlyconnected pump and wind driven driving fan therefor, the pump of whichis projected within the tank and, connected with a propelling powerplant, and the wind driven fan thereof projects Without the body ofthecraft in a position to be acted upon by the air rush incident tO flight.

' 17. In an aircraft fuel pumping system, a fuel storage tank locatedinteriorly' of the .body of the craft, a gravity feed tank locatedwithout and in a horizontal plane above the body of the craft, a fuelpump located interiorly of the storage tank, and driving meansdirect-connected with said storage tank" and including a fan locatedwithout the body air rush incident to flight. 18. A storage tank for.liquid fuel comprising a storage compartment, a" housing for a pumpinclosed in the storage compartment and submerged into the fuelcontained therein, and a partition subdividing the housing intonon-communicating compartments, one of which non-communicatingcompartments is provided with fuel inlet openings for admitting fuelthereinto from the storage compartment.

19. In an apparatus of the type set forth, a fuel storage tankcomprising a; storage compartment, a pump housing adapted to be.

inserted and submerged into the fuel contained in said storagecompartment, said housing being provided with means for flooding thelower portion thereof, a pump located in said flooded portion of thepump housingyand means arranged exterior-1y of the storage compartmentfor driving said p p- In testimony whereof I aflix my signature.

HENRY KLECKLER.

of the craft in the line of

